US10858092B2 - Flying object - Google Patents
Flying object Download PDFInfo
- Publication number
- US10858092B2 US10858092B2 US15/770,254 US201615770254A US10858092B2 US 10858092 B2 US10858092 B2 US 10858092B2 US 201615770254 A US201615770254 A US 201615770254A US 10858092 B2 US10858092 B2 US 10858092B2
- Authority
- US
- United States
- Prior art keywords
- protection member
- flying
- shaft member
- fuselage
- end portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 239000011358 absorbing material Substances 0.000 description 6
- 230000005611 electricity Effects 0.000 description 6
- 230000008602 contraction Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
- B64C15/12—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B64D27/26—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a flying object and, more particularly, to an improved flying object, which is provided with a plurality of rotor blade unit and thus can reduce the risk of a crash even if any one of the blades is damaged, thereby improving the flight stability.
- a helicopter is an aircraft flying by lift and propulsive force generated by the flow of air passing through the surfaces of rotor blades by rotating the rotor blades with engines, and includes the rotor blades, and an engine for driving the rotor blades, a clutch for connecting or disconnecting the transmission of the rotation of the engine between the rotor blades and the engine so as to prevent the rotor blades from stopping at the same time when the engine is broken, a decelerating device for decelerating the engine rotation to the most efficient number of rotations for the rotor blades, and a control unit for controlling the engine, the rotation of the rotor blades or the angle of the blades.
- FIG. 1 shows a typical one of the prior art helicopter, which includes a fuselage 2 , where not only people can board but also various devices can be equipped, rotor blades 4 for lifting and propelling the fuselage 2 , tail rotor blades 6 mounted on the rear portion of the fuselage 2 so as to rotate in a direction opposite to the rotation direction of the rotor blades 4 , thereby preventing the fuselage 2 from being rotated by the rotor blades 4 , and an engine (not shown) for driving the rotor blades 4 and the tail rotor blades 6 .
- the fuselage 2 is positioned close to the position where lift is generated by the rotor blades 4 such that in the case where the rotor blades 4 are applied with a resistance from the outside and suddenly turn, the fuselage 2 also makes a sudden turn, thereby degrading flight stability.
- the present invention has been derived to solve the above problems and has objectives as follows.
- the present invention has an objective to provide a flying object, in which a distance between a rotor blade unit and a fuselage is formed to be relatively longer than the rotation diameter of the rotor blade unit, thereby reducing the vibration transmitted to the fuselage due to the rotation of the rotor blade unit and improving flight stability.
- the present invention has an objective to provide a flying object, in which a plurality of rotor blade units are provided so as to prevent the risk of a crash even if any one of the rotor blade units is damaged during the flight.
- the present invention has an objective to provide a flying object, in which rotor blade units in rotation can be protected from the outside.
- the present invention has an objective to provide a flying object, of which falling can be prevented even if an engine is stopped.
- a flying object may include: a flying fuselage; a shaft member upwardly erected with a lower end portion fixed to the flying fuselage; a plate-shaped protection member fixed at the center portion thereof to the upper end portion of the shaft member and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means with respect to the plane surface of the protection member.
- the diameter of the protection member is A
- the interval between the rotation shafts of the rotor blade units facing each other is A1
- the length of the shaft member is B
- B+C 1.5A or B+C 1.5A1 may be satisfied.
- the shaft member may be formed from an expandable telescopic cylinder.
- a flying object in which a vertically elongated flying fuselage is provided instead of omitting the shaft member, includes: a flying fuselage; a protection member fixed on the upper end portion of the flying fuselage and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means with respect to the plane surface of the protection member.
- the driving means may be a jet engine or a rotor blade unit, and the through-holes and the driving means may be arranged such that four or more of the through-holes and four or more of the driving means are arranged at equal intervals respectively.
- each of the tilting means may include: a boss for rotatably coupling the rotation shaft of the rotor blade unit; a first actuator mounted on the top surface portion of the protection member and having a first rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; a second actuator mounted on the bottom surface portion of the protection member at the opposite side of the first actuator and having a second rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; a third actuator mounted on the top surface portion of the protection member at a right angle position with respect to the first actuator and having a third rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator and having a fourth rod capable of protruding and retracting with a
- each of the tilting means may include: a first actuator mounted on the top surface portion of the protection member and having a first rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; a second actuator mounted on the bottom surface portion of the protection member at the opposite side of the first actuator and having a second rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; a third actuator mounted on the top surface portion of the protection member at a right angle position with respect to the first actuator and having a third rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine, wherein the first actuator mounted on the top surface portion of the protection member and having a first
- a flying object includes: a flying fuselage; a shaft member upwardly erected with a lower end portion fixed to the flying fuselage; a plate-shaped protection member fixed at the center portion thereof to the upper end portion of the shaft member and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a rotation means for rotating the protection member with respect to the shaft member.
- the shaft member may be formed from an expandable telescopic cylinder.
- a flying object in which a vertically elongated flying fuselage is provided instead of omitting the shaft member, includes: a flying fuselage; a protection member fixed on the upper end portion of the flying fuselage and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a rotation means for rotating the protection member with respect to the flying fuselage, wherein if it is assumed that the diameter of the protection member is A, the interval between the rotation shafts of the rotor blade units facing each other is A1, and the length of the fuselage is C, formula C 1.5A or C 1.5A1 may be satisfied.
- the driving means may be a jet engine or a rotor blade unit, and the through-holes and the driving means may be arranged such that four or more of the through-holes and four or more of the driving means are arranged at equal intervals respectively.
- the rotation means may include: a first cylinder fixed on the shaft member and having a first rod rotatably coupled to the bottom surface of the protection member with an end portion thereof; a second cylinder fixed on the shaft member at a position facing the first cylinder and having a second rod rotatably coupled to the bottom surface of the protection member with an end portion thereof; a third cylinder fixed on the shaft member at a right angle position with respect to the first cylinder and having a third rod coupled to the bottom surface of the protection member with an end portion thereof; and a fourth cylinder fixed on the shaft member at a position facing the third cylinder and having a fourth rod rotatably coupled to the bottom surface of the protection member with an end portion thereof.
- the length of the shaft member is formed to be relatively longer than the rotation diameter of the rotor blade unit so that the vibration transmitted to the flying fuselage according to the rotation of the rotor blade unit is reduced as compared with that of the prior art flying object, and the heavy flying fuselage where passengers and an equipped engine are located is positioned below the rotor blade units with an interval equal to or larger than the rotation diameter of the rotor blade units so that the flight stability is improved.
- the shaft member is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture so as to enter the hangar after landing.
- a storage battery capable of storing the electricity generated from the engine is provided so as to drive the rotor blade unit and the tail rotor by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
- the plurality of rotor blade units are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units is damaged during the flight, and the rotating rotor blade unit can be protected by the protection member from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- FIG. 1 is a schematic view showing an example of the prior art flying object
- FIG. 2 is a schematic view showing a flying object according to the first embodiment of the present invention
- FIG. 3 is a perspective view showing the main parts of FIG. 2 .
- FIG. 4( a ) and FIG. 4( b ) are views showing the operation states of the main parts of the flying object according to the first embodiment of the present invention
- FIG. 5 is a schematic perspective view showing a flying object according to the second embodiment of the present invention.
- FIG. 6 is a schematic perspective view showing a flying object according to the third embodiment of the present invention.
- FIG. 7 is a schematic perspective view showing a flying object according to the fourth embodiment of the present invention.
- FIG. 8 is a schematic perspective view showing a flying object according to the fifth embodiment of the present invention.
- FIG. 9 is a schematic perspective view showing a flying object according to the sixth embodiment of the present invention.
- FIG. 10 is a schematic perspective view showing a flying object according to the seventh embodiment of the present invention.
- FIG. 11 is a schematic perspective view showing a flying object according to the eighth embodiment of the present invention.
- FIG. 12 is a schematic perspective view showing a flying object according to the ninth embodiment of the present invention.
- FIG. 13 is a perspective view showing the main parts of FIG. 12 .
- FIG. 14( a ) and FIG. 14( b ) are views showing the operation states of the main parts of the flying object according to the ninth embodiment of the present invention.
- FIG. 15 is a schematic perspective view showing a flying object according to the tenth embodiment of the present invention.
- FIG. 16 is a schematic perspective view showing a flying object according to the eleventh embodiment of the present invention.
- FIG. 17 is a schematic perspective view showing a flying object according to the twelfth embodiment of the present invention.
- FIG. 18 is a schematic perspective view showing a flying object according to the thirteenth embodiment of the present invention.
- FIG. 19 is a schematic perspective view showing a flying object according to the fourteenth embodiment of the present invention.
- FIG. 20 is a schematic perspective view showing a flying object according to the fifteenth embodiment of the present invention.
- FIG. 21 is a schematic perspective view showing a flying object according to the sixteenth embodiment of the present invention.
- a flying object according to the present invention has been developed to locate a flying fuselage at a position lower than that of a rotor blade unit or a jet engine with a considerable interval therebetween, thereby improving the flight stability, and provide a plurality of rotor blade units and jet engines, thereby reducing the risk of a crash even if any one of the rotor blade units or jet engines is damaged.
- a flying object includes a flying fuselage 10 with passengers on board and an engine equipped (not shown), a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, a plurality of rotor blade units 20 respectively arranged in each of the through-holes 51 so as to be driven to rotate by the power of the engine, and a tilting means for tilting each of the rotor blade units 20 with respect to the plane surface of the protection member 50 .
- the diameter of the protection member 50 is A and the length of the shaft member 30 is B, B A and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50 .
- the height of the flying fuselage 10 is C, B+C 1.5A.
- the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the rotation of the rotor blade unit 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
- the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
- the flying fuselage 10 is provided with a tail rotor 40 , which rotates in the opposite direction to that of the rotor blade units 20 .
- the tail rotor 40 rotates in the opposite direction to the rotation direction of the rotor blade units 20 .
- a storage battery (not shown) capable of storing the electricity generated from the engine is provided so as to drive the rotor blade units 20 and the tail rotor 40 by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
- the tilting means includes a boss 60 for rotatably coupling the rotation shaft of the rotor blade unit 20 , a first actuator 110 mounted on the top surface portion of the protection member 50 and having a first rod 111 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60 , a second actuator 120 mounted on the bottom surface portion of the protection member 50 at the opposite side of the first actuator 110 and having a second rod 121 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60 , a third actuator 130 mounted on the top surface portion of the protection member 50 at a right angle position with respect to the first actuator 110 and having a third rod 131 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60 , and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator 130 and having a fourth rod capable of protruding and retracting with
- Each motor 150 for driving and rotating each of the rotor blade units 20 is mounted on the boss 60 of each of the rotor blade units 20 , and each of the motors 150 is driven by the electricity, which is generated by the engine (not shown) and supplied from the storage battery (not shown).
- the rotor blade units 20 , the motors 150 , and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
- the rotor blade unit 50 is tilted while the boss 60 is tilted with respect to the third and fourth rods 131 , 141 by the operations of the first and second actuators 110 , 120 , thereby generating thrust.
- the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the supply of power by the storage battery is continued, thereby preventing a crash.
- the second embodiment has the same configuration as the first embodiment. Referring to FIG. 5 , the second embodiment has the characteristic configuration in that when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the shaft member 30 is B, B A1.
- the second embodiment has the characteristic configuration in that when assuming that the height of the flying fuselage 10 is C, B+C 1.5A1.
- the length of the shaft member 30 is formed to be longer than the interval A1 between the rotation shafts of the rotor blade units 20 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20 , thereby improving the flight stability.
- a flying object according to the third embodiment of the present invention will be explained below by applying the same reference signs to the same constituent elements as those of the flying object according the first embodiment of the present invention.
- the flying object includes a heavy flying fuselage 10 where passengers and an engine (not shown) are located, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine, and a rotation means for rotating the protection member 50 with respect to the shaft member 30 .
- the length of the shaft member 30 is formed to be long so that the vibration transmitted to the flying fuselage 10 according to the rotation of the rotor blade unit 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
- the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
- the flying fuselage 10 is provided with a tail rotor 40 , which rotates in the opposite direction to that of the rotor blade units 20 , wherein in order to prevent the flying fuselage 10 from rotating together when the rotor blade units 20 rotate in one direction and generate lift, the tail rotor 40 rotates in the opposite direction to the rotation direction of the rotor blade units 20 .
- a storage battery (not shown) capable of storing the electricity generated from the engine is provided so as to drive the rotor blade units 20 and the tail rotor 40 by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
- Each motor (not shown) for driving and rotating each of the rotor blade units 20 is mounted on the boss 60 of each of the rotor blade units 20 , and the motor is driven by the electricity, which is generated by the engine (not shown) and supplied from the storage battery (not shown).
- the rotor blade units 20 , the motors 150 , and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
- the rotation means includes a first cylinder 71 fixed on the shaft member 30 and having a first rod 71 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a second cylinder 72 fixed on the shaft member 30 at a position facing the first cylinder 71 and having a second rod 72 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a third cylinder 73 fixed on the shaft member 30 at a right angle position with respect to the first cylinder 71 and having a third rod 73 a coupled to the bottom surface of the protection member 50 with an end portion thereof, and a fourth cylinder 74 fixed on the shaft member 30 at a position facing the third cylinder 73 and having a fourth rod 74 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof.
- the rotation means is tilted by the expansion and contraction of each of the cylinders and, at this time, the rotor blade units 20 rotate and are tilted with respect to the shaft member 30 , thereby generating thrust.
- the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the supply of power by the storage battery is continued, thereby preventing a crash.
- the fourth embodiment has the same configuration as the third embodiment. Referring to FIG. 7 , the fourth embodiment has the characteristic configuration in that when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the shaft member 30 is B A1.
- the fourth embodiment has the characteristic configuration in that when assuming that the height of the flying fuselage 10 is C, B+C 1.5A1.
- the length of the shaft member 30 is formed to be longer than the interval A1 between the rotation shafts of the rotor blade units 20 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20 , thereby improving the flight stability.
- a flying object according to the fifth embodiment of the present invention includes: a flying fuselage 10 with passengers on board and an engine equipped (not shown), which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a tilting means for tilting each of the rotor blade unit 20 with respect to the plane surface of the protection member 50 .
- the fifth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the diameter of the protection member is A and the length of the flying fuselage is C, C 1.5A.
- the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 , thereby improving the flight stability.
- the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- the tilting means and the rest of the configuration are the same as those of the first embodiment, and the detailed description thereof will be omitted.
- a flying object according to the sixth embodiment of the present invention includes: a flying fuselage 10 with passengers on board and an engine equipped, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a tilting means for tilting each of the rotor blade unit 20 with respect to the plane surface of the protection member 50 .
- the sixth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the flying fuselage 10 is C, C 1.5A1.
- the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20 , thereby improving the flight stability.
- the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- the tilting means and the rest of the configuration are the same as those of the first embodiment, and the detailed description thereof will be omitted.
- a flying object according to the seventh embodiment of the present invention includes: a flying fuselage 10 with passengers on board and an engine equipped; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10 .
- the seventh embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 .
- the length C of the flying fuselage 10 is formed to be longer than the diameter A of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the ceiling of the flying fuselage 10 is formed to be high such that it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- the rotation means includes a first cylinder 71 fixed on the flying fuselage 10 and having a first rod 71 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a second cylinder 72 fixed on the flying fuselage 10 at a position facing the first cylinder 71 and having a second rod 72 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a third cylinder 73 fixed on the flying fuselage 10 at a right angle position with respect to the first cylinder 71 and having a third rod 73 a coupled to the bottom surface of the protection member 50 with an end portion thereof, and a fourth cylinder 74 fixed on the flying fuselage 10 at a position facing the third cylinder 73 and having a fourth rod 74 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof.
- the rotation means is tilted by the expansion and contraction of each of the cylinders and, at this time, the rotor blade units 20 rotate and are tilted with respect to the flying fuselage 10 , thereby generating thrust.
- each motor (not shown) for driving and rotating each of the rotor blade units 20 is provided for each of the rotor blade units 20 , and the motor is driven by the electricity, which is generated by the engine (not shown) and supplied from a storage battery (not shown).
- the rotor blade units 20 , the motors, and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
- the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- the supply of power by the storage battery is continued, thereby preventing a crash.
- a flying object according to the eighth embodiment of the present invention includes: a flying fuselage 10 with passengers on board and an engine equipped; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10 .
- the characteristic configuration of the eighth embodiment is that when the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the flying fuselage 10 is C, then C 1.5A1.
- the length of the flying fuselage 10 with respect to the protection member 50 is longer than that of the seventh embodiment, thereby further increasing the flight stability.
- the rotation means and the rest of the configuration are the same as those of the seventh embodiment, and the detailed description thereof will be omitted.
- a flying object according to the ninth embodiment of the present invention includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50 .
- the diameter of the protection member 50 is A and the length of the shaft member 30 is B, B A and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50 .
- the height of the flying fuselage 10 is C, B+C 1.5A.
- the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
- the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
- the tilting means includes a first actuator 110 mounted on the top surface portion of the protection member 50 and having a first rod 111 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200 , a second actuator 120 mounted on the bottom surface portion of the protection member 50 at the opposite side of the first actuator 110 and having a second rod 121 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200 , a third actuator 130 mounted on the top surface portion of the protection member 50 at a right angle position with respect to the first actuator 110 and having a third rod 131 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200 , and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator 130 and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200 .
- jet engines 200 four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
- the jet engine 200 is tilted by the operations of the first and second actuators 110 , 120 with respect to the third and fourth rods 131 , 141 , thereby generating thrust.
- the plurality of jet engines 200 are provided so that it is possible to prevent the risk of a crash even if any one of the jet engines 200 is damaged during the flight, and the jet engines 200 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
- a flying object includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50 .
- the tenth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 is A1 and the length of the shaft member 30 is B, then B A1 and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50 .
- the height of the flying fuselage 10 is C, B+C 1.5A1.
- the length of the shaft member 30 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
- the tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
- a flying object includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a rotation means for rotating the protection member 50 with respect to the shaft member 30 .
- the height of the flying fuselage 10 is C, B+C 1.5A.
- the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
- the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
- jet engines 200 four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
- the rotation means is the same as that of the third embodiment, and the detailed description thereof will be omitted.
- a flying object according to the twelfth embodiment of the present invention includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10 , a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a rotation means for rotating the protection member 50 with respect to the shaft member 30 .
- the twelfth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the shaft member 30 is B, then B A1.
- the height of the flying fuselage 10 is C, B+C 1.5A1.
- the length of the shaft member 30 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
- a flying object according to the thirteenth embodiment of the present invention includes a flying fuselage 10 with passengers on board, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each jet engine 200 arranged in each of the through-holes 51 ; and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50 .
- the thirteenth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the diameter of the protection member is A and the length of the flying fuselage 10 is C, C 1.5A.
- the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 , thereby improving the flight stability.
- the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- the tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
- a flying object according to the fourteenth embodiment of the present invention includes: a flying fuselage 10 with passengers on board, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each jet engine 200 arranged in each of the through-holes 51 ; and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50 .
- the fourteenth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the flying fuselage 10 is C, then C 1.5A1.
- the height of the flying fuselage 10 is C, B+C 1.5A1.
- the length of the flying fuselage 10 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
- the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- the tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
- a flying object according to the fifteenth embodiment of the present invention includes a flying fuselage 10 with passengers on board, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10 .
- the diameter of the protection member 50 is A and the length of the flying fuselage 10 is C, then C 1.5A, wherein the length of the flying fuselage 10 is formed to be relatively longer than the diameter of the protection member 50 and the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 .
- the length C of the flying fuselage 10 is formed to be longer than the diameter A of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the ceiling of the flying fuselage 10 is formed to be high such that it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
- jet engines 200 four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
- the rotation means is the same as that of the seventh embodiment, and the detailed description thereof will be omitted.
- a flying object includes a flying fuselage 10 with passengers on board, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51 , and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10 .
- the sixteenth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the flying fuselage 10 is C, then C 1.5A1.
- the length of the flying fuselage 10 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.
Description
The present invention relates to a flying object and, more particularly, to an improved flying object, which is provided with a plurality of rotor blade unit and thus can reduce the risk of a crash even if any one of the blades is damaged, thereby improving the flight stability.
In general, a helicopter is an aircraft flying by lift and propulsive force generated by the flow of air passing through the surfaces of rotor blades by rotating the rotor blades with engines, and includes the rotor blades, and an engine for driving the rotor blades, a clutch for connecting or disconnecting the transmission of the rotation of the engine between the rotor blades and the engine so as to prevent the rotor blades from stopping at the same time when the engine is broken, a decelerating device for decelerating the engine rotation to the most efficient number of rotations for the rotor blades, and a control unit for controlling the engine, the rotation of the rotor blades or the angle of the blades.
However, the typical prior art helicopter has the following problems.
First, there is a problem that the length of a rotation shaft 4 a is considerably short as compared with the rotation diameter of the rotor blades 4 such that the vibration transmitted to the fuselage 2 due to the rotation of the rotor blades 4 is significant, thereby lowering the boarding feeling.
Second, there is another problem that the fuselage 2 is positioned close to the position where lift is generated by the rotor blades 4 such that in the case where the rotor blades 4 are applied with a resistance from the outside and suddenly turn, the fuselage 2 also makes a sudden turn, thereby degrading flight stability.
Third, there is a further problem that only one rotor blade unit 4 is provided such that there is the risk of a crash when the rotation of the rotor blade unit 4 is stopped during the flight due to the damage, which is generated to the rotor blade unit 4 from the outside, the engine stop and the like.
The present invention has been derived to solve the above problems and has objectives as follows.
First, the present invention has an objective to provide a flying object, in which a distance between a rotor blade unit and a fuselage is formed to be relatively longer than the rotation diameter of the rotor blade unit, thereby reducing the vibration transmitted to the fuselage due to the rotation of the rotor blade unit and improving flight stability.
Second, the present invention has an objective to provide a flying object, in which a plurality of rotor blade units are provided so as to prevent the risk of a crash even if any one of the rotor blade units is damaged during the flight.
Third, the present invention has an objective to provide a flying object, in which rotor blade units in rotation can be protected from the outside.
Fourth, the present invention has an objective to provide a flying object, of which falling can be prevented even if an engine is stopped.
A flying object according to an embodiment of the present invention may include: a flying fuselage; a shaft member upwardly erected with a lower end portion fixed to the flying fuselage; a plate-shaped protection member fixed at the center portion thereof to the upper end portion of the shaft member and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means with respect to the plane surface of the protection member.
Herein, if it is assumed that the diameter of the protection member is A, the interval between the rotation shafts of the rotor blade units facing each other is A1, and the length of the shaft member is B, BA or BA1 may be satisfied.
Meanwhile, if it is assumed that the height of the flying fuselage is C, B+C1.5A or B+C1.5A1 may be satisfied.
Herein, the shaft member may be formed from an expandable telescopic cylinder.
According to another embodiment, in which a vertically elongated flying fuselage is provided instead of omitting the shaft member, a flying object according to this embodiment of the present invention includes: a flying fuselage; a protection member fixed on the upper end portion of the flying fuselage and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means with respect to the plane surface of the protection member.
Herein, if it is assumed that the diameter of the protection member is A, the interval between the rotation shafts of the rotor blade units facing each other is A1, and the length of the fuselage is C, formula C1.5A or C1.5A1 may be satisfied.
In the above two embodiments, the driving means may be a jet engine or a rotor blade unit, and the through-holes and the driving means may be arranged such that four or more of the through-holes and four or more of the driving means are arranged at equal intervals respectively.
In the above two embodiments, if the driving means is a rotor blade unit, each of the tilting means may include: a boss for rotatably coupling the rotation shaft of the rotor blade unit; a first actuator mounted on the top surface portion of the protection member and having a first rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; a second actuator mounted on the bottom surface portion of the protection member at the opposite side of the first actuator and having a second rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; a third actuator mounted on the top surface portion of the protection member at a right angle position with respect to the first actuator and having a third rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss; and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss, wherein the boss is tilted by the operations of the third and fourth actuators or the first and second actuators with respect to the first and second rods or the third and fourth rods such that the rotor blade unit can be tilted.
In the above two embodiments, if the driving means is a jet engine, each of the tilting means may include: a first actuator mounted on the top surface portion of the protection member and having a first rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; a second actuator mounted on the bottom surface portion of the protection member at the opposite side of the first actuator and having a second rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; a third actuator mounted on the top surface portion of the protection member at a right angle position with respect to the first actuator and having a third rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine; and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine, wherein the jet engine may be tilted with respect to the protection member by the operations of the third and fourth actuators or the first and second actuators with respect to the first and second rods or the third and fourth rods.
Meanwhile, according to still another embodiment, in which a rotation means is provided instead of a tilting means, a flying object according to this embodiment of the present invention includes: a flying fuselage; a shaft member upwardly erected with a lower end portion fixed to the flying fuselage; a plate-shaped protection member fixed at the center portion thereof to the upper end portion of the shaft member and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a rotation means for rotating the protection member with respect to the shaft member.
Herein, if it is assumed that the diameter of the protection member is A, the interval between the rotation shafts of the rotor blade units facing each other is A1, and the length of the shaft member is B, formula BA or BA1 may be satisfied, and if it is assumed that the height of the flying fuselage is C, formula B+C1.5A or B+C1.5A1 may be satisfied.
Also, the shaft member may be formed from an expandable telescopic cylinder.
According to a further embodiment, in which a vertically elongated flying fuselage is provided instead of omitting the shaft member, a flying object according to this embodiment of the present invention includes: a flying fuselage; a protection member fixed on the upper end portion of the flying fuselage and having a plurality of through-holes formed in the same circumference thereof; each driving means arranged in each of the through-holes; and a rotation means for rotating the protection member with respect to the flying fuselage, wherein if it is assumed that the diameter of the protection member is A, the interval between the rotation shafts of the rotor blade units facing each other is A1, and the length of the fuselage is C, formula C1.5A or C1.5A1 may be satisfied.
In the last two embodiments, the driving means may be a jet engine or a rotor blade unit, and the through-holes and the driving means may be arranged such that four or more of the through-holes and four or more of the driving means are arranged at equal intervals respectively.
In the last two embodiments, the rotation means may include: a first cylinder fixed on the shaft member and having a first rod rotatably coupled to the bottom surface of the protection member with an end portion thereof; a second cylinder fixed on the shaft member at a position facing the first cylinder and having a second rod rotatably coupled to the bottom surface of the protection member with an end portion thereof; a third cylinder fixed on the shaft member at a right angle position with respect to the first cylinder and having a third rod coupled to the bottom surface of the protection member with an end portion thereof; and a fourth cylinder fixed on the shaft member at a position facing the third cylinder and having a fourth rod rotatably coupled to the bottom surface of the protection member with an end portion thereof.
First, according to the flying object of the present invention, the length of the shaft member is formed to be relatively longer than the rotation diameter of the rotor blade unit so that the vibration transmitted to the flying fuselage according to the rotation of the rotor blade unit is reduced as compared with that of the prior art flying object, and the heavy flying fuselage where passengers and an equipped engine are located is positioned below the rotor blade units with an interval equal to or larger than the rotation diameter of the rotor blade units so that the flight stability is improved.
Second, the shaft member is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture so as to enter the hangar after landing.
Third, a storage battery capable of storing the electricity generated from the engine is provided so as to drive the rotor blade unit and the tail rotor by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
Fourth, the plurality of rotor blade units are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units is damaged during the flight, and the rotating rotor blade unit can be protected by the protection member from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
A flying object according to the present invention has been developed to locate a flying fuselage at a position lower than that of a rotor blade unit or a jet engine with a considerable interval therebetween, thereby improving the flight stability, and provide a plurality of rotor blade units and jet engines, thereby reducing the risk of a crash even if any one of the rotor blade units or jet engines is damaged.
A flying object according to the first embodiment of the present invention, as shown in FIG. 2 to FIG. 4 , includes a flying fuselage 10 with passengers on board and an engine equipped (not shown), a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, a plurality of rotor blade units 20 respectively arranged in each of the through-holes 51 so as to be driven to rotate by the power of the engine, and a tilting means for tilting each of the rotor blade units 20 with respect to the plane surface of the protection member 50.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the shaft member 30 is B, BA and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50.
In this case, the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the rotation of the rotor blade unit 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
In addition, the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
In addition, the flying fuselage 10 is provided with a tail rotor 40, which rotates in the opposite direction to that of the rotor blade units 20.
In order to prevent the flying fuselage 10 from rotating together when the rotor blade units 20 rotate in one direction and generate lift, the tail rotor 40 rotates in the opposite direction to the rotation direction of the rotor blade units 20.
In addition, a storage battery (not shown) capable of storing the electricity generated from the engine is provided so as to drive the rotor blade units 20 and the tail rotor 40 by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
The tilting means includes a boss 60 for rotatably coupling the rotation shaft of the rotor blade unit 20, a first actuator 110 mounted on the top surface portion of the protection member 50 and having a first rod 111 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60, a second actuator 120 mounted on the bottom surface portion of the protection member 50 at the opposite side of the first actuator 110 and having a second rod 121 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60, a third actuator 130 mounted on the top surface portion of the protection member 50 at a right angle position with respect to the first actuator 110 and having a third rod 131 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss 60, and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator 130 and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the boss.
Each motor 150 for driving and rotating each of the rotor blade units 20 is mounted on the boss 60 of each of the rotor blade units 20, and each of the motors 150 is driven by the electricity, which is generated by the engine (not shown) and supplied from the storage battery (not shown).
Meanwhile, the rotor blade units 20, the motors 150, and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
Referring to FIG. 4(a) and FIG. 4(b) , in the tilting means described above, the rotor blade unit 50 is tilted while the boss 60 is tilted with respect to the third and fourth rods 131, 141 by the operations of the first and second actuators 110, 120, thereby generating thrust.
According to the flying object as configured above, the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash. In addition, even if the engine is stopped, the supply of power by the storage battery is continued, thereby preventing a crash.
The second embodiment has the same configuration as the first embodiment. Referring to FIG. 5 , the second embodiment has the characteristic configuration in that when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the shaft member 30 is B, BA1.
In addition, the second embodiment has the characteristic configuration in that when assuming that the height of the flying fuselage 10 is C, B+C1.5A1.
In this case, the length of the shaft member 30 is formed to be longer than the interval A1 between the rotation shafts of the rotor blade units 20 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20, thereby improving the flight stability.
A flying object according to the third embodiment of the present invention will be explained below by applying the same reference signs to the same constituent elements as those of the flying object according the first embodiment of the present invention.
Referring to FIG. 6 , the flying object includes a heavy flying fuselage 10 where passengers and an engine (not shown) are located, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine, and a rotation means for rotating the protection member 50 with respect to the shaft member 30.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the shaft member 30 is B, then BA and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50.
In this case, the length of the shaft member 30 is formed to be long so that the vibration transmitted to the flying fuselage 10 according to the rotation of the rotor blade unit 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
In addition, the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
In addition, the flying fuselage 10 is provided with a tail rotor 40, which rotates in the opposite direction to that of the rotor blade units 20, wherein in order to prevent the flying fuselage 10 from rotating together when the rotor blade units 20 rotate in one direction and generate lift, the tail rotor 40 rotates in the opposite direction to the rotation direction of the rotor blade units 20.
In addition, a storage battery (not shown) capable of storing the electricity generated from the engine is provided so as to drive the rotor blade units 20 and the tail rotor 40 by the storage battery when the engine is unexpectedly stopped during the flight, thereby preventing the risk of a crash.
Each motor (not shown) for driving and rotating each of the rotor blade units 20 is mounted on the boss 60 of each of the rotor blade units 20, and the motor is driven by the electricity, which is generated by the engine (not shown) and supplied from the storage battery (not shown).
Meanwhile, the rotor blade units 20, the motors 150, and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
The rotation means includes a first cylinder 71 fixed on the shaft member 30 and having a first rod 71 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a second cylinder 72 fixed on the shaft member 30 at a position facing the first cylinder 71 and having a second rod 72 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a third cylinder 73 fixed on the shaft member 30 at a right angle position with respect to the first cylinder 71 and having a third rod 73 a coupled to the bottom surface of the protection member 50 with an end portion thereof, and a fourth cylinder 74 fixed on the shaft member 30 at a position facing the third cylinder 73 and having a fourth rod 74 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof.
As the protection member 50 is rotated with respect to the shaft member 30, the rotation means is tilted by the expansion and contraction of each of the cylinders and, at this time, the rotor blade units 20 rotate and are tilted with respect to the shaft member 30, thereby generating thrust.
According to the flying object as configured above, the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash. In addition, even if the engine is stopped, the supply of power by the storage battery is continued, thereby preventing a crash.
The fourth embodiment has the same configuration as the third embodiment. Referring to FIG. 7 , the fourth embodiment has the characteristic configuration in that when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the shaft member 30 is BA1.
In addition, the fourth embodiment has the characteristic configuration in that when assuming that the height of the flying fuselage 10 is C, B+C1.5A1.
In this case, the length of the shaft member 30 is formed to be longer than the interval A1 between the rotation shafts of the rotor blade units 20 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20, thereby improving the flight stability.
A flying object according to the fifth embodiment of the present invention, as shown in FIG. 8 , includes: a flying fuselage 10 with passengers on board and an engine equipped (not shown), which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a tilting means for tilting each of the rotor blade unit 20 with respect to the plane surface of the protection member 50.
The fifth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the diameter of the protection member is A and the length of the flying fuselage is C, C1.5A.
In this case, the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50, thereby improving the flight stability.
Particularly, since the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
The tilting means and the rest of the configuration are the same as those of the first embodiment, and the detailed description thereof will be omitted.
A flying object according to the sixth embodiment of the present invention, as shown in FIG. 9 , includes: a flying fuselage 10 with passengers on board and an engine equipped, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a tilting means for tilting each of the rotor blade unit 20 with respect to the plane surface of the protection member 50.
The sixth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the flying fuselage 10 is C, C1.5A1.
In this case, the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an equipped engine are located is positioned below the rotor blade units 20 and the protection member 50 with an interval equal to or larger than the interval A1 between the rotation shafts of the rotor blade units 20, thereby improving the flight stability.
Particularly, since the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
The tilting means and the rest of the configuration are the same as those of the first embodiment, and the detailed description thereof will be omitted.
A flying object according to the seventh embodiment of the present invention, as shown in FIG. 10 , includes: a flying fuselage 10 with passengers on board and an engine equipped; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the flying fuselage 10 is C, then C1.5A, and the seventh embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50.
In this case, the length C of the flying fuselage 10 is formed to be longer than the diameter A of the protection member 50 so that the vibration transmitted to the flying fuselage 10 due to the rotation of the rotor blade units 20 is reduced as compared with that of the prior art flying object, and the ceiling of the flying fuselage 10 is formed to be high such that it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
The rotation means includes a first cylinder 71 fixed on the flying fuselage 10 and having a first rod 71 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a second cylinder 72 fixed on the flying fuselage 10 at a position facing the first cylinder 71 and having a second rod 72 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof, a third cylinder 73 fixed on the flying fuselage 10 at a right angle position with respect to the first cylinder 71 and having a third rod 73 a coupled to the bottom surface of the protection member 50 with an end portion thereof, and a fourth cylinder 74 fixed on the flying fuselage 10 at a position facing the third cylinder 73 and having a fourth rod 74 a rotatably coupled to the bottom surface of the protection member 50 with an end portion thereof.
As the protection member 50 is rotated with respect to the flying fuselage 10, the rotation means is tilted by the expansion and contraction of each of the cylinders and, at this time, the rotor blade units 20 rotate and are tilted with respect to the flying fuselage 10, thereby generating thrust.
In addition, each motor (not shown) for driving and rotating each of the rotor blade units 20 is provided for each of the rotor blade units 20, and the motor is driven by the electricity, which is generated by the engine (not shown) and supplied from a storage battery (not shown).
The rotor blade units 20, the motors, and the storage batteries are provided in four or more respectively so that stable flight can be achieved even if any one of them fails during the flight.
According to the flying object as configured above, the plurality of rotor blade units 20 are provided so that it is possible to prevent the risk of a crash even if any one of the rotor blade units 20 is damaged during the flight, and the rotating rotor blade units 20 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash. In addition, even if the engine is stopped, the supply of power by the storage battery is continued, thereby preventing a crash.
A flying object according to the eighth embodiment of the present invention, as shown in FIG. 11 , includes: a flying fuselage 10 with passengers on board and an engine equipped; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each rotor blade unit 20 arranged in each of the through-holes 51 and rotating with the power of the engine; and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10.
Unlike the seventh embodiment, the characteristic configuration of the eighth embodiment is that when the interval between the rotation shafts of the rotor blade units 20 facing each other is A1 and the length of the flying fuselage 10 is C, then C1.5A1.
In this case, the length of the flying fuselage 10 with respect to the protection member 50 is longer than that of the seventh embodiment, thereby further increasing the flight stability.
The rotation means and the rest of the configuration are the same as those of the seventh embodiment, and the detailed description thereof will be omitted.
A flying object according to the ninth embodiment of the present invention, as shown in FIG. 12 to FIG. 14 , includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the shaft member 30 is B, BA and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50.
In this case, the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
In addition, the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
The tilting means includes a first actuator 110 mounted on the top surface portion of the protection member 50 and having a first rod 111 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200, a second actuator 120 mounted on the bottom surface portion of the protection member 50 at the opposite side of the first actuator 110 and having a second rod 121 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200, a third actuator 130 mounted on the top surface portion of the protection member 50 at a right angle position with respect to the first actuator 110 and having a third rod 131 capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200, and a fourth actuator mounted on the bottom surface portion of the protection member at the opposite side of the third actuator 130 and having a fourth rod capable of protruding and retracting with a free end portion rotatably coupled to the outer surface of the jet engine 200.
Meanwhile, as for the jet engines 200, four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
Referring to FIG. 14(a) and FIG. 14(b) , by the tilting means described above, the jet engine 200 is tilted by the operations of the first and second actuators 110, 120 with respect to the third and fourth rods 131, 141, thereby generating thrust.
According to the flying object as configured above, the plurality of jet engines 200 are provided so that it is possible to prevent the risk of a crash even if any one of the jet engines 200 is damaged during the flight, and the jet engines 200 can be protected by the protection member 50 from external force and thus prevented from being damaged, thereby preventing the risk of a crash.
Referring to FIG. 15 , a flying object according to the tenth embodiment of the present invention includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50.
Herein, compared with the ninth embodiment, the tenth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 is A1 and the length of the shaft member 30 is B, then BA1 and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50.
In this case, the length of the shaft member 30 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
The tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
Referring to FIG. 16 , a flying object according to the eleventh embodiment of the present invention includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a rotation means for rotating the protection member 50 with respect to the shaft member 30.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the shaft member 30 is B, then BA and thus the length of the shaft member 30 is formed to be relatively longer than the diameter of the protection member 50.
In this case, the length of the shaft member 30 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50 so that the flight stability is improved.
In addition, the shaft member 30 is formed as a telescopic cylinder so as to be expandable, so that the flying object can maintain a stable stopping posture and enter the hangar by reducing the length of the shaft member 30 after landing.
Meanwhile, as for the jet engines 200, four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
The rotation means is the same as that of the third embodiment, and the detailed description thereof will be omitted.
The twelfth embodiment has the same configuration as the eleventh embodiment. Referring to FIG. 17 , a flying object according to the twelfth embodiment of the present invention includes a flying fuselage 10 with passengers on board, a shaft member 30 upwardly erected with a lower end portion fixed to the flying fuselage 10, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the shaft member 30 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a rotation means for rotating the protection member 50 with respect to the shaft member 30.
The twelfth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the shaft member 30 is B, then BA1.
In this case, the length of the shaft member 30 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
The rotation means and the rest of the configuration are the same as those of the eleventh embodiment, and the detailed description thereof will be omitted.
A flying object according to the thirteenth embodiment of the present invention, as shown in FIG. 18 , includes a flying fuselage 10 with passengers on board, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each jet engine 200 arranged in each of the through-holes 51; and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50.
The thirteenth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and when assuming that the diameter of the protection member is A and the length of the flying fuselage 10 is C, C1.5A.
In this case, the length of the flying fuselage 10 is formed to be longer than the diameter of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where passengers and an engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the diameter of the protection member 50, thereby improving the flight stability.
Particularly, since the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
The tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
A flying object according to the fourteenth embodiment of the present invention, as shown in FIG. 19 , includes: a flying fuselage 10 with passengers on board, which is formed to be vertically elongated; a protection member 50 fixed on the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof; each jet engine 200 arranged in each of the through-holes 51; and a tilting means for tilting each of the jet engines 200 with respect to the protection member 50.
The fourteenth embodiment has the characteristic configuration in that the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50 and if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the flying fuselage 10 is C, then C1.5A1.
In this case, the length of the flying fuselage 10 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
Particularly, since the ceiling of the flying fuselage 10 is formed to be high, it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
The tilting means and the rest of the configuration are the same as those of the ninth embodiment, and the detailed description thereof will be omitted.
A flying object according to the fifteenth embodiment of the present invention, as shown in FIG. 20 , includes a flying fuselage 10 with passengers on board, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10.
Herein, if it is assumed that the diameter of the protection member 50 is A and the length of the flying fuselage 10 is C, then C1.5A, wherein the length of the flying fuselage 10 is formed to be relatively longer than the diameter of the protection member 50 and the flying fuselage 10 with passengers on board and the engine equipped is directly connected to the protection member 50.
In this case, the length C of the flying fuselage 10 is formed to be longer than the diameter A of the protection member 50 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the ceiling of the flying fuselage 10 is formed to be high such that it is advantageous to install a sound absorbing material (not shown) and to secure a boarding space for passengers standing.
Meanwhile, as for the jet engines 200, four or more jet engines 200 are provided at a uniform interval so that stable flight can be achieved even if any one of them fails during the flight.
The rotation means is the same as that of the seventh embodiment, and the detailed description thereof will be omitted.
The sixteenth embodiment has the same configuration as the fifteenth embodiment. Referring to FIG. 21 , a flying object includes a flying fuselage 10 with passengers on board, a plate-shaped protection member 50 fixed at the center portion thereof to the upper end portion of the flying fuselage 10 and having a plurality of through-holes 51 formed in the same circumference thereof, jet engines 200 respectively arranged in each of the through-holes 51, and a rotation means for rotating the protection member 50 with respect to the flying fuselage 10.
The sixteenth embodiment has the characteristic configuration in that if it is assumed that the interval between the jet engines 200 facing each other is A1 and the length of the flying fuselage 10 is C, then C1.5A1.
In this case, the length of the flying fuselage 10 is formed to be longer than the interval A1 between the jet engines 200 so that the vibration transmitted to the flying fuselage 10 according to the operation of the jet engines 200 is reduced as compared with that of the prior art flying object, and the heavy flying fuselage 10 where the passengers and the equipped engine are located is positioned below the jet engines 200 and the protection member 50 with an interval equal to or larger than the interval A1 between the jet engines 200 so that the flight stability is improved.
The rotation means and the rest of the configuration are the same as those of the fifteenth embodiment, and the detailed description thereof will be omitted.
Claims (6)
1. A flying object, comprising:
a flying fuselage;
a shaft member upwardly erected with a lower end portion fixed to the flying fuselage;
a plate-shaped protection member having a center portion fixed to an upper end portion of the shaft member and having a plurality of holes that each are located at an equal radial distance from a center of the plate-shaped protection member;
a plurality of driving means, each of the plurality of driving means being arranged in a corresponding one of the plurality of holes; and
a rotation means for rotating the plate-shaped protection member with respect to the shaft member,
wherein each of the plurality of driving means is a jet engine or a rotor blade unit, and
wherein a diameter of the plate-shaped protection member is A, two driving means of the plurality of driving means are located opposite with respect to the center of the plate-shaped protection member and an interval between centers of the two driving means is A1, a length of the shaft member is B, and a formula B>A or B>A1 is satisfied.
2. The flying object according to claim 1 , wherein the shaft member is formed from a telescopic cylinder so as to be expanded and contracted.
3. The flying object according to claim 1 , wherein the plurality of holes and the plurality of driving means are arranged such that four or more of the plurality of holes and four or more of the plurality of driving means are arranged at equal intervals along a circumferential direction of the plate-shaped protection member, respectively.
4. The flying object according to claim 1 , wherein the rotation means includes:
a first cylinder fixed on the shaft member and having a first rod rotatably coupled to a bottom surface of the protection member with an end portion thereof;
a second cylinder fixed on the shaft member at a position facing the first cylinder and having a second rod rotatably coupled to the bottom surface of the protection member with an end portion thereof;
a third cylinder fixed on the shaft member at a right angle position with respect to the first cylinder and having a third rod coupled to the bottom surface of the protection member with an end portion thereof; and
a fourth cylinder fixed on the shaft member at a position facing the third cylinder and having a fourth rod rotatably coupled to the bottom surface of the protection member with an end portion thereof.
5. The flying object according to claim 1 , wherein if the height of the flying fuselage is C, B+C>1.5A or B+C>1.5A1.
6. The flying object according to claim 5 , wherein the rotation means includes:
a first cylinder fixed on the shaft member and having a first rod rotatably coupled to a bottom surface of the protection member with an end portion thereof;
a second cylinder fixed on the shaft member at a position facing the first cylinder and having a second rod rotatably coupled to the bottom surface of the protection member with an end portion thereof;
a third cylinder fixed on the shaft member at a right angle position with respect to the first cylinder and having a third rod coupled to the bottom surface of the protection member with an end portion thereof; and
a fourth cylinder fixed on the shaft member at a position facing the third cylinder and having a fourth rod rotatably coupled to the bottom surface of the protection member with an end portion thereof.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020150155253A KR101627680B1 (en) | 2015-11-05 | 2015-11-05 | Airplane structure |
KR10-2015-0155253 | 2015-11-05 | ||
PCT/KR2016/012249 WO2017078330A1 (en) | 2015-11-05 | 2016-10-28 | Flying object |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/KR2016/012249 A-371-Of-International WO2017078330A1 (en) | 2015-11-05 | 2016-10-28 | Flying object |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US17/086,210 Division US11634215B2 (en) | 2015-11-05 | 2020-10-30 | Flying object |
Publications (2)
Publication Number | Publication Date |
---|---|
US20180312246A1 US20180312246A1 (en) | 2018-11-01 |
US10858092B2 true US10858092B2 (en) | 2020-12-08 |
Family
ID=56193192
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/770,254 Active 2037-04-02 US10858092B2 (en) | 2015-11-05 | 2016-10-28 | Flying object |
US17/086,210 Active 2037-07-13 US11634215B2 (en) | 2015-11-05 | 2020-10-30 | Flying object |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US17/086,210 Active 2037-07-13 US11634215B2 (en) | 2015-11-05 | 2020-10-30 | Flying object |
Country Status (8)
Country | Link |
---|---|
US (2) | US10858092B2 (en) |
EP (1) | EP3372496A4 (en) |
JP (1) | JP6770068B2 (en) |
KR (1) | KR101627680B1 (en) |
CN (1) | CN108349586A (en) |
AU (2) | AU2016348095C1 (en) |
CA (1) | CA3002368C (en) |
WO (1) | WO2017078330A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20200324889A1 (en) * | 2017-12-15 | 2020-10-15 | Seoul National University R&Db Foundation | Flight vehicle |
US11613347B1 (en) * | 2021-11-22 | 2023-03-28 | Defang Yuan | Low cost, high reliable, double engined VTOL |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109436313A (en) * | 2018-12-21 | 2019-03-08 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
JP6755596B2 (en) * | 2019-03-11 | 2020-09-16 | 株式会社プロドローン | Rotorcraft |
CN113734437B (en) * | 2021-10-19 | 2023-10-03 | 重庆航天工业有限公司 | Automatic tilting device of electric helicopter |
Citations (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3176774A (en) * | 1963-07-24 | 1965-04-06 | William V Krinsky | Helicopter drive control |
US5505407A (en) * | 1993-09-09 | 1996-04-09 | Fran Rich Chi Associates | Air-land vehicle |
US5746390A (en) * | 1996-03-20 | 1998-05-05 | Fran Rich Chi Associates, Inc. | Air-land vehicle with ducted fan vanes providing improved performance |
US6138943A (en) * | 1998-12-11 | 2000-10-31 | Huang; Yung-Chi | Foldable ascending/descending wing stand for flying apparatus |
KR20000067382A (en) | 1999-04-28 | 2000-11-15 | 장근호 | Airship direction control system |
US20040167682A1 (en) * | 2003-02-21 | 2004-08-26 | Lockheed Martin Corporation | Virtual sensor mast |
KR20110032974A (en) | 2009-09-24 | 2011-03-30 | 조효석 | Air plane spinning wing by jet engine |
KR20110055842A (en) | 2009-11-20 | 2011-05-26 | 순천대학교 산학협력단 | The flying object equipped coaxial duct system |
KR101129249B1 (en) | 2011-11-22 | 2012-06-12 | 조금배 | A vertical takeoff and landing aircraft |
KR20120136797A (en) | 2011-06-10 | 2012-12-20 | 드림스페이스월드주식회사 | Safety cover for unmanned vehicle |
US20130206919A1 (en) * | 2010-11-12 | 2013-08-15 | Gabriel Shachor | Systems and methods for controlling an aerial unit |
WO2017172402A1 (en) * | 2016-03-28 | 2017-10-05 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
US9896199B2 (en) * | 2013-12-20 | 2018-02-20 | Bell Helicopter Textron Inc. | Rotor hub for a rotorcraft |
EP3549858A1 (en) * | 2018-04-06 | 2019-10-09 | Prades Imasd, S.L. | Flying apparatus |
US20190322368A1 (en) * | 2018-04-24 | 2019-10-24 | Thomas W. Melcher | Electric Vertical Takeoff and Landing Aircraft |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1964179A (en) * | 1928-03-19 | 1934-06-26 | Trew F Poole | Airplane |
US4795111A (en) * | 1987-02-17 | 1989-01-03 | Moller International, Inc. | Robotic or remotely controlled flying platform |
KR930023532A (en) * | 1992-05-30 | 1993-12-21 | 이헌조 | Automatic Water Level Control Circuit and Method of Automatic Washing Machine |
JPH09142392A (en) * | 1995-11-17 | 1997-06-03 | Yoshiyuki Matsuda | Flying vehicle |
CN1115261C (en) * | 1999-12-17 | 2003-07-23 | 林康 | Helicopter-type vehicle with cyclone gyro for space and land |
CA2455075C (en) * | 2001-08-06 | 2010-07-20 | Eric Ashworth | Propulsion linearizing mechanism |
US9493235B2 (en) * | 2002-10-01 | 2016-11-15 | Dylan T X Zhou | Amphibious vertical takeoff and landing unmanned device |
US20070187547A1 (en) | 2003-10-23 | 2007-08-16 | Kelly Patrick D | Vertical Lifting of Airplanes to Flying Heights |
CA2459200A1 (en) * | 2004-02-27 | 2005-08-27 | John S. Lamont | Aircraft |
US7802755B2 (en) * | 2004-03-10 | 2010-09-28 | Poltorak Alexander I | Rotating wing aircraft with tip-driven rotor and rotor guide-ring |
US7887011B1 (en) * | 2007-01-18 | 2011-02-15 | Baldwin G Douglas | Apparatus and methods for carrying airborne cargo |
CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | A composite rotating fixed-wing aircraft and its design method |
WO2011023834A1 (en) * | 2009-08-26 | 2011-03-03 | Munoz Saiz Manuel | Lift, thrust and stabiliser system for vertical take-off and landing aircraft |
US8738198B2 (en) * | 2011-05-26 | 2014-05-27 | Foster-Miller, Inc. | Robot surveillance system and method |
US20150286216A1 (en) * | 2012-10-31 | 2015-10-08 | The University Of Tokushima | Conveyance device and control method for flight vehicle |
JPWO2014203593A1 (en) * | 2013-06-21 | 2017-02-23 | 株式会社エルム | Remotely controlled unmanned air vehicle control system |
AT515456B1 (en) * | 2014-02-18 | 2018-04-15 | Iat 21 Innovative Aeronautics Tech Gmbh | aircraft |
US9862487B2 (en) * | 2014-05-23 | 2018-01-09 | Aibotix GmbH | Remote-controlled platform shaped aircraft |
US10988263B2 (en) * | 2016-12-08 | 2021-04-27 | Thomas Francis Daily, JR. | VTOL aircraft with jet engine coupled to downward thrust nozzles |
CN107757844B (en) * | 2017-10-21 | 2019-05-28 | 天津黎明时代信息技术有限公司 | It is a kind of marine to track down and arrest and relief unmanned plane |
-
2015
- 2015-11-05 KR KR1020150155253A patent/KR101627680B1/en active IP Right Grant
-
2016
- 2016-10-28 CN CN201680064703.8A patent/CN108349586A/en active Pending
- 2016-10-28 US US15/770,254 patent/US10858092B2/en active Active
- 2016-10-28 AU AU2016348095A patent/AU2016348095C1/en not_active Ceased
- 2016-10-28 WO PCT/KR2016/012249 patent/WO2017078330A1/en active Application Filing
- 2016-10-28 JP JP2018519832A patent/JP6770068B2/en active Active
- 2016-10-28 EP EP16862346.0A patent/EP3372496A4/en not_active Withdrawn
- 2016-10-28 CA CA3002368A patent/CA3002368C/en active Active
-
2020
- 2020-08-28 AU AU2020223755A patent/AU2020223755A1/en not_active Abandoned
- 2020-10-30 US US17/086,210 patent/US11634215B2/en active Active
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3176774A (en) * | 1963-07-24 | 1965-04-06 | William V Krinsky | Helicopter drive control |
US5505407A (en) * | 1993-09-09 | 1996-04-09 | Fran Rich Chi Associates | Air-land vehicle |
US5746390A (en) * | 1996-03-20 | 1998-05-05 | Fran Rich Chi Associates, Inc. | Air-land vehicle with ducted fan vanes providing improved performance |
US6138943A (en) * | 1998-12-11 | 2000-10-31 | Huang; Yung-Chi | Foldable ascending/descending wing stand for flying apparatus |
KR20000067382A (en) | 1999-04-28 | 2000-11-15 | 장근호 | Airship direction control system |
US20040167682A1 (en) * | 2003-02-21 | 2004-08-26 | Lockheed Martin Corporation | Virtual sensor mast |
US7149611B2 (en) * | 2003-02-21 | 2006-12-12 | Lockheed Martin Corporation | Virtual sensor mast |
KR20110032974A (en) | 2009-09-24 | 2011-03-30 | 조효석 | Air plane spinning wing by jet engine |
KR20110055842A (en) | 2009-11-20 | 2011-05-26 | 순천대학교 산학협력단 | The flying object equipped coaxial duct system |
US20130206919A1 (en) * | 2010-11-12 | 2013-08-15 | Gabriel Shachor | Systems and methods for controlling an aerial unit |
US20130214088A1 (en) * | 2010-11-12 | 2013-08-22 | Gabriel Shachor | Aerial unit and method for elevating payloads |
KR20120136797A (en) | 2011-06-10 | 2012-12-20 | 드림스페이스월드주식회사 | Safety cover for unmanned vehicle |
KR101129249B1 (en) | 2011-11-22 | 2012-06-12 | 조금배 | A vertical takeoff and landing aircraft |
US9896199B2 (en) * | 2013-12-20 | 2018-02-20 | Bell Helicopter Textron Inc. | Rotor hub for a rotorcraft |
WO2017172402A1 (en) * | 2016-03-28 | 2017-10-05 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
EP3549858A1 (en) * | 2018-04-06 | 2019-10-09 | Prades Imasd, S.L. | Flying apparatus |
US20190322368A1 (en) * | 2018-04-24 | 2019-10-24 | Thomas W. Melcher | Electric Vertical Takeoff and Landing Aircraft |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20200324889A1 (en) * | 2017-12-15 | 2020-10-15 | Seoul National University R&Db Foundation | Flight vehicle |
US11560223B2 (en) * | 2017-12-15 | 2023-01-24 | Seoul National University R&Db Foundation | Flight vehicle |
US11613347B1 (en) * | 2021-11-22 | 2023-03-28 | Defang Yuan | Low cost, high reliable, double engined VTOL |
Also Published As
Publication number | Publication date |
---|---|
US20180312246A1 (en) | 2018-11-01 |
AU2016348095B2 (en) | 2020-10-01 |
CA3002368C (en) | 2020-02-11 |
AU2016348095A1 (en) | 2018-05-17 |
EP3372496A4 (en) | 2019-05-08 |
JP6770068B2 (en) | 2020-10-14 |
US11634215B2 (en) | 2023-04-25 |
AU2016348095C1 (en) | 2021-01-14 |
CN108349586A (en) | 2018-07-31 |
AU2020223755A1 (en) | 2020-09-17 |
WO2017078330A1 (en) | 2017-05-11 |
US20210229801A1 (en) | 2021-07-29 |
KR101627680B1 (en) | 2016-06-07 |
CA3002368A1 (en) | 2017-05-11 |
EP3372496A1 (en) | 2018-09-12 |
JP2018531835A (en) | 2018-11-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US11634215B2 (en) | Flying object | |
US7959104B2 (en) | Flying device with improved movement on the ground | |
US10647419B1 (en) | Unmanned aerial vehicle configuration | |
US11111009B1 (en) | Operating multirotor aircraft with enhanced yaw control | |
US10518875B2 (en) | Vertical take-off aircraft | |
US11535371B2 (en) | Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft | |
US10392107B2 (en) | Aerial vehicle capable of vertical take-off and landing, vertical and horizontal flight and on-air energy generation | |
CA3003641C (en) | Redundant aircraft propulsion system using multiple motors per drive shaft | |
JP2017074804A (en) | Multi-rotor helicopter | |
JP3677748B1 (en) | Aircraft created by fixing the rapid airflow generating wind direction changing device directly on the side or side wall of the aircraft. | |
JP2019501830A (en) | Hybrid propelled vertical take-off and landing aircraft | |
US9272779B2 (en) | Aircraft with pivoting rotor mast | |
CN105000180B (en) | Aerodynamic configuration of aircraft device | |
EP3357812B1 (en) | Variable in-flight wing fold system | |
KR20170094045A (en) | A multicopter type smart drone using tilt rotor | |
JP2019112050A (en) | Air vehicle | |
WO2007010682A1 (en) | Rotor with shroud storable into and extendable from outside of bottom plate and aircraft having the rotor with shroud | |
WO2023182127A1 (en) | Flying apparatus | |
KR102129368B1 (en) | A drone with adjustable distance between rotors | |
KR102287049B1 (en) | The redirection apparatus of unmanned aerial vehicle and unmanned aerial vehicle having the same | |
CN107902080A (en) | Unmanned plane structure and there is stealthy unmanned plane | |
KR101150855B1 (en) | Flying Control Structure for Duct Type Flying Robot t | |
CN206766342U (en) | A kind of foldable rotor support of unmanned plane | |
WO2021019557A1 (en) | Vertical rotor assembly | |
CN115723977A (en) | Vertical take-off and landing unmanned aerial vehicle rotor wing positioning and accommodating mechanism |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
FEPP | Fee payment procedure |
Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: MICROENTITY |
|
FEPP | Fee payment procedure |
Free format text: ENTITY STATUS SET TO MICRO (ORIGINAL EVENT CODE: MICR); ENTITY STATUS OF PATENT OWNER: MICROENTITY |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NON FINAL ACTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NON FINAL ACTION MAILED |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |